Hostname: page-component-5cf477f64f-tx7qf Total loading time: 0 Render date: 2025-04-03T05:34:16.160Z Has data issue: false hasContentIssue false
  • English
  • Français

The Displacement of the Nose Shock Wave from a Pitot Tube under a Streamwise Velocity Gradient

Published online by Cambridge University Press:  04 July 2016

D. Sloan
D. Sloan*
Affiliation:
Fluid Mechanics Division, Dept of Mechanical Engineering, University of Liverpool
Get access Rights & Permissions [Opens in a new window]

Summary:—

The pressure reading of a pitot tube in a supersonic flow corresponds to the position of the nose shock wave. Results of measurements of the shock stand-off distance are presented for three different streamwise Mach number gradients and for a uniform flow. These results are compared with existing theoretical values.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 71 , Issue 682 , October 1967 , pp. 725 - 726
Copyright
Copyright © Royal Aeronautical Society 1967

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

1.Quincey, V. G. and Callinan, J.Experiments with a Pitot Rake at M=l.50. Journal of the Royal Aeronautical Society, Vol 67, No 636, p 793, December 1963.CrossRefGoogle Scholar
2.Moeckel, W. E. Approximate Methods for Predicting Form and Location of Detached Shock Waves Ahead of Plane or Axially Symmetric Bodies. NACA TN 1921, 1949.Google Scholar